CN103437913A - Metal diaphragm storage box made of carbon-fiber composite materials and manufacturing method thereof - Google Patents
Metal diaphragm storage box made of carbon-fiber composite materials and manufacturing method thereof Download PDFInfo
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Abstract
The invention provides a metal diaphragm storage box made of carbon-fiber composite materials and a manufacturing method thereof. The metal diaphragm storage box comprises a liner 1 and a metal diaphragm 2 and also comprises an insulating layer 3 and a carbon-fiber composite material layer 4, wherein the liner 1 comprises an upper flange 11, an upper hemisphere 12, a connecting ring 13, a lower hemisphere 14 and a lower flange 15; the upper hemisphere 12 and the lower hemisphere 14 are connected by the connecting ring 13; the upper flange 11 is connected with the upper hemisphere 12; the lower flange 15 is connected with the lower hemisphere 14; the metal diaphragm 2 is butted with the connecting ring 13; the outer surface of the liner 1 is coated with the insulating layer 3; the outer surface of the insulating layer 3 is wound with the carbon-fiber composite material layer 4, and is connected with the carbon-fiber composite material layer 4 in a bonding manner. The metal diaphragm storage box provided by the invention has the advantages that the problems of large weight and low structure efficiency of the metal diaphragm storage box are solved, the light-weight design of the metal diaphragm storage box is realized, the cost is reduced and the performance of a product is improved.
Description
Technical field
The present invention relates to a kind of pressurized container, particularly, relate to a kind of carbon fiber composite Metal diaphragm tank and manufacture method thereof.
Background technique
Propellant tank is a kind of mesolow pressurized container of carrying liqs management apparatus, for liquid appearance control power system, designs.The key issue of this kind of product is: be will possess under the space microgravity condition liquid is carried out to the effectively ability (gas-liquid isolation) of management on the one hand; To want to bear the mechanical environment examination (mechanics overload etc.) of delivery when emission on the other hand.
Propellant tank management apparatus commonly used has surface tension, metal diaphragm and nonmetal capsule formula etc.The main feature of Metal diaphragm tank is: utilize metal diaphragm to carry out active management to propellant agent: on the one hand, under the effect of extruding gas, diaphragm is close to liquid level, has eliminated rocking of propellant agent, and design proposal guarantees that the rolling power of tank filling medium meets the demands; Utilize on the other hand metal diaphragm by gas-liquid physics every edge, guarantee to export the not propellant agent of gas enclosure to motor.This kind of metal diaphragm is connected the employing Type of Welding with the tank housing, guarantee that propellant agent sealed type storage performance meets the demands.
Strategy and tactics guided missile model and spacecraft are selected the tank of Metal diaphragm tank as its propulsion system in a large number both at home and abroad.But these products are all containers of all metal construction, along with the development of aerospace cause, this product can not meet the requirement of aircraft lighting design far away.
In recent years the fast development of composite technology, the especially extensive application of high-performance carbon fibre winding technology in pressurized container, the reduction that it is large the architecture quality of container.But because Metal diaphragm tank is generally the globular pressure-container of many circumferential welded seams, the intrinsic many places Geometrical discontinuity that exists in structure.The unresolved composite technology that uses in Metal diaphragm tank of existing technology.
The patent of invention of Europe publication number EP0941925A2 discloses a kind of propellant tank, but this invention is only the basic configuration that has provided Metal diaphragm tank, fails to solve the lighting design problem of product.
The patent of invention of China Patent Publication No. CN102275067 discloses the preparation for processing of a kind of astrovehicle fuel with the hemisphere metallic tank, the method has provided the manufacture method of titanium material metal diaphragm, easily control quality, but, the method adopts pure titanium sheet metal as preparing material, expensive, really apply and have certain difficulty.
The patent of invention of China publication number CN1715729A discloses composite material pressure container and the manufacture method thereof of a kind of large scale, super thin metal inner lining.There is following limitation in this invention: at first, how this invention assembles the metal diaphragm management apparatus if not relating to; Secondly, if the tank of this invention after the large quality propellant agent of filling, its mechanical environment adaptive capacity is limited, this invention does not provide the technological approaches how to address this problem, and this invention winding technology does not provide the embodiment of globular pressure-container.
Summary of the invention
For defect of the prior art, the purpose of this invention is to provide a kind of carbon fiber composite Metal diaphragm tank and manufacture method thereof.
According to an aspect of the present invention, a kind of carbon fiber composite Metal diaphragm tank is provided, comprise liner 1 and metal diaphragm 2, also comprise isolation layer 3 and carbon fiber composite layer 4, liner 1 comprises upper flange 11, episphere 12, connecting ring 13, lower semisphere 14 and lower flange 15, episphere 12 is connected by connecting ring 13 with lower semisphere 14, upper flange 11 is connected with episphere 12, lower flange 15 is connected with lower semisphere 14, metal diaphragm 2 docks with connecting ring 13, the outer surface of liner 1 is coated with insulating layer coating 3, isolation layer 3 outer surfaces are wound around carbon fiber composite layer 4, and the outer surface of isolation layer 3 is connected with carbon fiber composite layer 4 is bonding.
Preferably, metal diaphragm 2 adopts argon arc welding to be welded to connect with connecting ring 13.
Preferably, liner 1 adopts aluminum alloy to make, and the thickness T 1 of liner 1 is 1.2～1.7mm, and the diameter D1 of liner 1 is 800～1200mm.Episphere 12, connecting ring 13 and lower semisphere 14 are welded to connect successively, and joint wall thickness T 2 is 2～3mm; Upper flange 11 and episphere 12, reach lower flange 14 and lower semisphere 15 and all adopt and be welded to connect, and docking location diameter D2 is 50～300mm.
Preferably, episphere 12 ends of liner 1 are provided with chamfering R1, and lower semisphere 14 ends are provided with chamfering R2, wherein, chamfering R1 is not less than 10mm, and chamfering R2 is not less than 15mm, and the thickness T 3 that chamfering R1 is corresponding is not less than 8mm, thickness T 4 corresponding to chamfering R2 is for being not less than 10mm; Liner 1 top and bottom wall thickness respectively by T3 and T4 gradually transition be thinned to T1, and transition diameter D3 is not less than 300mm, transition diameter D4 is not less than 400mm.
Preferably, isolation layer 3 is polyester PU7022 coating, and its thickness is 0.1～0.5mm.
Preferably, carbon fiber composite layer 4 is carbon fiber/epoxy winding layer.
Preferably, carbon fiber/epoxy winding layer is mixed into glue by epoxy resin and anhydride curing agent, benzyl dimethylamine according to the ratio of weight proportion 1:0.9:0.005, then the carbon fiber after impregnation is wound around and is prepared from the outer surface of liner 1.
According to another aspect of the present invention, provide a kind of manufacture method of carbon fiber composite Metal diaphragm tank, comprise the following steps:
Step 1: manufacture processing liner 1 and liner 1 and metal diaphragm 2 butt welding are connected together;
Step 2: the outer surface at liner coats isolation layer 3;
Step 3: the carbon fiber composite layer 4 that is wound around impregnation at isolation layer 3 outer surfaces.
Preferably, in step 1, the manufacture method of liner 1 comprises the following steps:
Step 11: episphere and lower semisphere rotary press modelling: at first use oxygen-acetylene welding torch rifle preheating core and plectane blank to carry out 100～200 ℃ of preheatings, then concentrate blank heating to 350 to spinning roller spinning below and wide 35～40mm position, spinning roller the place ahead～450 ℃, spinning speed is 250～500r/min, the depth of cut is 0.3～0.7mm/r, oxygen in spinning process-acetylene welding torch rifle and spinning roller synchronizing moving, and control 350～450 ℃ of above-mentioned blank temperature positions, the episphere 12 that finally to be spun to diameter be 800～1500mm and the blank of lower semisphere 14;
Step 11: episphere and lower semisphere heat treatment: head formed by spinning is heat-treated, and treatment temperature is: 380 ± 10 ℃, and processing time 60 ± 5min, cooling with stove.
Step 12: episphere and lower semisphere roughing: the spinning part is fixed on rough turn frock and carries out rough turn processing, stay machining allowance 1～1.5mm;
Step 13: profile in episphere and lower semisphere fine finishing: rough turn hemisphere is fixed on the special tooling be complementary with the hemisphere outer mold surface in finish turning to profile to the product requirement size;
Step 14: episphere and lower semisphere fine finishing outer mold surface: by hemisphere be fixed on finish turning on the special tooling that is complementary of profile the finish turning outer mold surface to the product requirement size;
Step 15: electron beam welding: by upper flange and episphere, lower semisphere and lower flange adopt electron beam welding to be connected together, and vacuum degree in vacuum chamber is not more than 7 * 10
-4mbar, welding current is 80～160A, speed is 30mm/s;
Step 16: argon arc welding welding:
Adopt argon arc welding to weld together episphere and connecting ring, welding current is 60～70A, and welding speed is 165～185mm/min, and argon flow amount is 8～10L/min, and wire feed rate is 200～300mmmm/min, and the gage of wire 3mm trade mark is LF14;
Adopt argon arc welding to weld together metal diaphragm and connecting ring, welding current is 30～50A, and welding speed is 120～140mm/min, and argon flow amount is 8～10L/min, and wire feed rate is 200～300mm/min, and the gage of wire 3mm trade mark is LF14;
Adopt argon arc welding to weld together connecting ring and lower semisphere, welding current is 90～100A, and welding speed is 165～185mm/min, and argon flow amount is 8～10L/min, and wire feed rate is 200～300mmmm/min, and the gage of wire 3mm trade mark is LF14;
Step 17: liner integrally annealed: the liner 1 that will complete through abovementioned steps carries out annealing in process, and standard is 380 ± 10 ℃/4h, cooling with stove.
Preferably, step 3 comprises the following steps:
Step 31: the liner outer surface is processed: the outer surface of liner is carried out to grinding process with 80～120 purpose sand paper, then the surface after polishing with the cleaning of acetone reagent;
Step 32: carbon fiber resin pickup glue: according to the ratio of weight and number extracting epoxy resin: anhydride curing agent: benzyl dimethylamine=1:0.08～0.1:0.005～0.006 mixed preparing resin glue, by carbon fiber resin pickup glue;
Step 33: carbon fiber composite is wound around: adopt plane to be wound around form, be respectively from inside to outside five layers of vertical winding and one deck ring with being wound around, first layer adopts the plane winding, and winding utmost point bore dia is 50～140mm, and thickness is 0.12mm; The second layer adopts plane to be wound around, and being wound around utmost point bore dia is 270mm, and thickness is 0.18mm; The 3rd layer adopts plane to be wound around, and being wound around utmost point bore dia is 370～500mm, and thickness is 0.24mm; The 4th layer adopts plane to be wound around, and being wound around utmost point bore dia is 610～740mm, and thickness is 0.34mm; Layer 5 adopts plane to be wound around, and being wound around utmost point bore dia is 750～980mm, and thickness is 0.42mm; Layer 6 adopts hoop to be wound around, and width is not less than 80mm, and thickness is 0.5mm.
Step 34: solidify and surfacing: the liner 1 that will be wound with carbon fiber composite layer 4 is warmed up to 120 ± 5 ℃, is incubated 50～70min, cooling with stove.
Carbon fiber composite Metal diaphragm tank of the present invention has the following advantages:
1 carbon fiber composite Metal diaphragm tank, solved the lighting problem of product, than the structure efficiency PV/G of common metal diaphragm tank (P: the working pressure of Metal diaphragm tank; V: the volume of Metal diaphragm tank; G: the weight of Metal diaphragm tank) more than improving twice;
2 products simple in structure, anufacturability is good, cost is low, the cycle is short;
3 for many welding line structures, have carried out optimal design on the wall thickness dimension of product, have guaranteed the technique exploitativeness of weld seam and final Weld Performance, have guaranteed to be wound around the fatigue behaviour of tank;
4 have adopted the partial structurtes design at the upper and lower two ends of tank, are guaranteeing that on the little basis of tank weight change, the mechanical environment of product is adaptable, and Product Level bears quiet overload and is not less than 5t, and the axial static overload is not less than 12t.
Carbon fiber composite Metal diaphragm tank manufacture method of the present invention has the following advantages:
1 interior outer mold surface processing method has guaranteed that the high wall thickness scattered error of machining accuracy of large diameter thin wall global shell is no more than 0.1mm, and spherical shell circularity is not more than 0.1mm;
The structure property high-tensile that 2 spinning process have improved metallic material is not less than 350MPa, and yield strength is not less than 170MPa, and specific elongation is not less than 25%;
The rational selection of 3 welding conditions, guaranteed that the weld seam first-time qualification rate reaches 95%, and secondary repair welding up-to-standard rate reaches 100%, has also guaranteed that the amount of deformation of liner is little, is conducive to the distortion coupling of liner and carbon fiber, improves the fatigue behaviour of product;
4 resin systems and proportioning parameter have been carried out preferably, are wound around the more conventional raising 20% of performance coefficient that the definite winding process parameter of scheme simulation analysis has guaranteed fiber.
In sum, adopt the present invention can solve the Metal diaphragm tank quality large, structure efficiency PV/G (P: the working pressure of Metal diaphragm tank; V: the volume of Metal diaphragm tank; G: the weight of Metal diaphragm tank) low problem, solve the technical problem that existing Filament Wound Composite technology can't be applied to the Metal diaphragm tank field, realize Metal diaphragm tank lighting design, solve product and can not adapt to delivery transmitter section mechanical environment adaptability problem, and the present invention has also solved the difficult problem that major diameter metal diaphragm tank is manufactured, optimize manufacturing process, fallen at the end cost, improved product performance.
The accompanying drawing explanation
By reading the detailed description of non-limiting example being done with reference to the following drawings, it is more obvious that other features, objects and advantages of the present invention will become:
The structural representation that Fig. 1 is a kind of carbon fiber composite Metal diaphragm tank;
The partial structurtes enlarged diagram that Fig. 2 is liner in Fig. 1.
Embodiment
Below in conjunction with specific embodiment, the present invention is described in detail.Following examples will contribute to those skilled in the art further to understand the present invention, but not limit in any form the present invention.It should be pointed out that to those skilled in the art, without departing from the inventive concept of the premise, can also make some distortion and improvement.These all belong to protection scope of the present invention.
Refer to Fig. 1, a kind of carbon fiber composite Metal diaphragm tank, comprise liner 1 and metal diaphragm 2, also comprises isolation layer 3 and carbon fiber composite layer 4.
Liner 1 comprises upper flange 11, episphere 12, connecting ring 13, lower semisphere 14 and lower flange 15, episphere 12 is connected by connecting ring 13 with lower semisphere 14, upper flange 11 is connected with episphere 12, lower flange 15 is connected with lower semisphere 14, metal diaphragm 2 docks with connecting ring 13, the outer surface of liner 1 is coated with insulating layer coating 3, and isolation layer 3 outer surfaces are wound around carbon fiber composite layer 4, and the outer surface of isolation layer 3 is connected with carbon fiber composite layer 4 is bonding.
Further, metal diaphragm 2 adopts argon arc welding to be welded to connect with connecting ring 13.Episphere 12, connecting ring 13 and lower semisphere 14 are welded to connect successively, and joint wall thickness T 2 is 2～3mm; Upper flange 11 and episphere 12, reach lower flange 14 and lower semisphere 15 and all adopt and be welded to connect, and docking location diameter D2 is 50～300mm.
Further, liner 1 adopts aluminum alloy to make, and the thickness T 1 of liner 1 is 1.2～1.7mm, and the diameter D1 of liner 1 is 800～1200mm.Episphere 12 ends of liner 1 are provided with chamfering R1, and lower semisphere 14 ends are provided with chamfering R2, and wherein, chamfering R1 is not less than 10mm, and chamfering R2 is not less than 15mm, and thickness T 3 corresponding to chamfering R1 be not less than 8mm, and thickness T 4 corresponding to chamfering R2 is for being not less than 10mm; Liner 1 top and bottom wall thickness respectively by T3 and T4 gradually transition be thinned to T1, and transition diameter D3 is not less than 300mm, transition diameter D4 is not less than 400mm.
Further, isolation layer 3 is polyester PU7022 coating, and its thickness is 0.1～0.5mm.
Further, carbon fiber composite layer 4 is carbon fiber/epoxy winding layer.Particularly, carbon fiber/epoxy winding layer is mixed into glue by epoxy resin and anhydride curing agent, benzyl dimethylamine according to the ratio of weight proportion 1:0.9:0.005, then the carbon fiber after impregnation is wound around and is prepared from the outer surface of liner 1.
The present invention also provides a kind of manufacture method of carbon fiber composite Metal diaphragm tank, comprises the following steps:
Step 1: manufacture processing liner 1 and liner 1 and metal diaphragm 2 butt welding are connected together.
Particularly, the manufacture method of liner 1 comprises the following steps:
Step 11: episphere and lower semisphere rotary press modelling: at first use oxygen-acetylene welding torch rifle preheating core and plectane blank to carry out 100～200 ℃ of preheatings, then concentrate blank heating to 350 to spinning roller spinning below and wide 35～40mm position, spinning roller the place ahead～450 ℃, spinning speed is 250～500r/min, the depth of cut is 0.3～0.7mm/r, oxygen in spinning process-acetylene welding torch rifle and spinning roller synchronizing moving, and control 350～450 ℃ of above-mentioned blank temperature positions, the episphere 12 that finally to be spun to diameter be 800～1500mm and the blank of lower semisphere 14;
Step 11: episphere and lower semisphere heat treatment: head formed by spinning is heat-treated, and treatment temperature is: 380 ± 10 ℃, and processing time 60 ± 5min, cooling with stove.
Step 12: episphere and lower semisphere roughing: the spinning part is fixed on rough turn frock and carries out rough turn processing, stay machining allowance 1～1.5mm;
Step 13: profile in episphere and lower semisphere fine finishing: rough turn hemisphere is fixed on the special tooling be complementary with the hemisphere outer mold surface in finish turning to profile to the product requirement size;
Step 14: episphere and lower semisphere fine finishing outer mold surface: by hemisphere be fixed on finish turning on the special tooling that is complementary of profile the finish turning outer mold surface to the product requirement size;
Step 15: electron beam welding: by upper flange and episphere, lower semisphere and lower flange adopt electron beam welding to be connected together, and vacuum degree in vacuum chamber is not more than 7 * 10
-4mbar, welding current is 80～160A, speed is 30mm/s;
Step 16: argon arc welding welding:
Adopt argon arc welding to weld together episphere and connecting ring, welding current is 60～70A, and welding speed is 165～185mm/min, and argon flow amount is 8～10L/min, and wire feed rate is 200～300mmmm/min, and the gage of wire 3mm trade mark is LF14;
Adopt argon arc welding to weld together metal diaphragm and connecting ring, welding current is 30～50A, and welding speed is 120～140mm/min, and argon flow amount is 8～10L/min, and wire feed rate is 200～300mm/min, and the gage of wire 3mm trade mark is LF14;
Adopt argon arc welding to weld together connecting ring and lower semisphere, welding current is 90～100A, and welding speed is 165～185mm/min, and argon flow amount is 8～10L/min, and wire feed rate is 200～300mmmm/min, and the gage of wire 3mm trade mark is LF14;
Step 17: liner integrally annealed: the liner 1 that will complete through abovementioned steps carries out annealing in process, and standard is 380 ± 10 ℃/4h, cooling with stove.
Step 2: the outer surface at liner coats isolation layer 3;
Step 3: the carbon fiber composite layer 4 that is wound around impregnation at isolation layer 3 outer surfaces.
Particularly, liner 1 outer surface winding carbon fiber composite layer 4 is realized by following steps:
Step 31: the liner outer surface is processed: the outer surface of liner is carried out to grinding process with 80～120 purpose sand paper, then the surface after polishing with the cleaning of acetone reagent;
Step 32: carbon fiber resin pickup glue: according to the ratio of weight and number extracting epoxy resin: anhydride curing agent: benzyl dimethylamine=1:0.08～0.1:0.005～0.006 mixed preparing resin glue, by carbon fiber resin pickup glue;
Step 33: carbon fiber composite is wound around: adopt plane to be wound around form, be respectively from inside to outside five layers of vertical winding and one deck ring with being wound around, first layer adopts the plane winding, and winding utmost point bore dia is 50～140mm, and thickness is 0.12mm; The second layer adopts plane to be wound around, and being wound around utmost point bore dia is 270mm, and thickness is 0.18mm; The 3rd layer adopts plane to be wound around, and being wound around utmost point bore dia is 370～500mm, and thickness is 0.24mm; The 4th layer adopts plane to be wound around, and being wound around utmost point bore dia is 610～740mm, and thickness is 0.34mm; Layer 5 adopts plane to be wound around, and being wound around utmost point bore dia is 750～980mm, and thickness is 0.42mm; Layer 6 adopts hoop to be wound around, and width is not less than 80mm, and thickness is 0.5mm.
Step 34: solidify and surfacing: the liner 1 that will be wound with carbon fiber composite layer 4 is warmed up to 120 ± 5 ℃, is incubated 50～70min, cooling with stove.
Above specific embodiments of the invention are described.It will be appreciated that, the present invention is not limited to above-mentioned specific implementations, and those skilled in the art can make various distortion or modification within the scope of the claims, and this does not affect flesh and blood of the present invention.
Claims (10)
1. a carbon fiber composite Metal diaphragm tank, comprise: liner (1) and metal diaphragm (2), it is characterized in that, also comprise isolation layer (3) and carbon fiber composite layer (4), described liner (1) comprises upper flange (11), episphere (12), connecting ring (13), lower semisphere (14) and lower flange (15), described episphere (12) is connected by connecting ring (13) with lower semisphere (14), described upper flange (11) is connected with described episphere (12), described lower flange (15) is connected with described lower semisphere (14), described metal diaphragm (2) docks with described connecting ring (13), the outer surface of described liner (1) applies described isolation layer (3), described isolation layer (3) outer surface is wound around described carbon fiber composite layer (4), and the outer surface of described isolation layer (3) and bonding connection of described carbon fiber composite layer (4).
2. carbon fiber composite Metal diaphragm tank according to claim 1, is characterized in that, described metal diaphragm (2) adopts argon arc welding to be welded to connect with described connecting ring (13).
3. carbon fiber composite Metal diaphragm tank according to claim 1, it is characterized in that, described liner (1) adopts aluminum alloy to make, and the thickness (T1) of described liner (1) is 1.2～1.7mm, and the diameter (D1) of liner (1) is 800～1200mm.Described episphere (12), connecting ring (13) and lower semisphere (14) are welded to connect successively, and joint wall thickness (T2) is 2～3mm; The above flange (11) and episphere (12), reach lower flange (14) and lower semisphere (15) and all adopt and be welded to connect, and docking location diameter (D2) is 50～300mm.
4. carbon fiber composite Metal diaphragm tank according to claim 1, it is characterized in that, episphere (12) end of described liner (1) is provided with chamfering (R1), lower semisphere (14) end is provided with chamfering (R2), wherein, described chamfering (R1) is not less than 10mm, described chamfering (R2) is not less than 15mm, and thickness (T3) corresponding to described chamfering (R1) is not less than 8mm, the thickness (T4) of described chamfering (R2) correspondence is for being not less than 10mm; Described liner (1) top and bottom wall thickness respectively by T3 and T4 gradually transition be thinned to T1, and transition diameter (D3) is not less than 300mm, transition diameter (D4) is not less than 400mm.
5. carbon fiber composite Metal diaphragm tank according to claim 1, is characterized in that, described isolation layer (3) is polyester PU7022 coating, and its thickness is 0.1～0.5mm.
6. carbon fiber composite Metal diaphragm tank according to claim 1, is characterized in that, described carbon fiber composite layer (4) is carbon fiber/epoxy winding layer.
7. carbon fiber composite Metal diaphragm tank according to claim 1, it is characterized in that, described carbon fiber/epoxy winding layer is mixed into glue by epoxy resin and anhydride curing agent, benzyl dimethylamine according to the ratio of weight proportion 1:0.9:0.005, then the carbon fiber after impregnation is wound around and is prepared from the outer surface of liner (1).
8. the manufacture method of a carbon fiber composite Metal diaphragm tank, is characterized in that, comprises the following steps:
Step 1: manufacture processing liner (1) and liner (1) and metal diaphragm (2) butt welding are connected together;
Step 2: the outer surface at liner coats isolation layer (3);
Step 3: the carbon fiber composite layer (4) that is wound around impregnation at isolation layer (3) outer surface.
9. the manufacture method of carbon fiber composite Metal diaphragm tank according to claim 8, is characterized in that, the manufacture method of liner in step 1 (1) comprises the following steps:
Step 11: episphere and lower semisphere rotary press modelling: at first use oxygen-acetylene welding torch rifle preheating core and plectane blank to carry out 100～200 ℃ of preheatings, then concentrate blank heating to 350 to spinning roller spinning below and wide 35～40mm position, spinning roller the place ahead～450 ℃, spinning speed is 250～500r/min, the depth of cut is 0.3～0.7mm/r, oxygen in spinning process-acetylene welding torch rifle and spinning roller synchronizing moving, and control 350～450 ℃ of above-mentioned blank temperature positions, the episphere (12) that finally to be spun to diameter be 800～1500mm and the blank of lower semisphere (14);
Step 11: episphere and lower semisphere heat treatment: head formed by spinning is heat-treated, and treatment temperature is: 380 ± 10 ℃, and processing time 60 ± 5min, cooling with stove.
Step 12: episphere and lower semisphere roughing: the spinning part is fixed on rough turn frock and carries out rough turn processing, stay machining allowance 1～1.5mm;
Step 13: profile in episphere and lower semisphere fine finishing: rough turn hemisphere is fixed on the special tooling be complementary with the hemisphere outer mold surface in finish turning to profile to the product requirement size;
Step 14: episphere and lower semisphere fine finishing outer mold surface: by hemisphere be fixed on finish turning on the special tooling that is complementary of profile the finish turning outer mold surface to the product requirement size;
Step 15: electron beam welding: by upper flange and episphere, lower semisphere and lower flange adopt electron beam welding to be connected together, and vacuum degree in vacuum chamber is not more than 7 * 10
-4mbar, welding current is 80～160A, speed is 30mm/s;
Step 16: argon arc welding welding:
Adopt argon arc welding to weld together episphere and connecting ring, welding current is 60～70A, and welding speed is 165～185mm/min, and argon flow amount is 8～10L/min, and wire feed rate is 200～300mmmm/min, and the gage of wire 3mm trade mark is LF14;
Adopt argon arc welding to weld together metal diaphragm and connecting ring, welding current is 30～50A, and welding speed is 120～140mm/min, and argon flow amount is 8～10L/min, and wire feed rate is 200～300mm/min, and the gage of wire 3mm trade mark is LF14;
Adopt argon arc welding to weld together connecting ring and lower semisphere, welding current is 90～100A, and welding speed is 165～185mm/min, and argon flow amount is 8～10L/min, and wire feed rate is 200～300mmmm/min, and the gage of wire 3mm trade mark is LF14;
Step 17: liner integrally annealed: the liner that will complete through abovementioned steps (1) carries out annealing in process, and standard is 380 ± 10 ℃/4h, cooling with stove.
10. the manufacture method of carbon fiber composite Metal diaphragm tank according to claim 8, is characterized in that, step 3 comprises the following steps:
Step 31: the liner outer surface is processed: the outer surface of liner is carried out to grinding process with 80～120 purpose sand paper, then the surface after polishing with the cleaning of acetone reagent;
Step 32: carbon fiber resin pickup glue: according to the ratio of weight and number extracting epoxy resin: anhydride curing agent: benzyl dimethylamine=1:0.08～0.1:0.005～0.006 mixed preparing resin glue, by carbon fiber resin pickup glue;
Step 33: carbon fiber composite is wound around: adopt plane to be wound around form, be respectively from inside to outside five layers of vertical winding and one deck ring with being wound around, first layer adopts the plane winding, and winding utmost point bore dia is 50～140mm, and thickness is 0.12mm; The second layer adopts plane to be wound around, and being wound around utmost point bore dia is 270mm, and thickness is 0.18mm; The 3rd layer adopts plane to be wound around, and being wound around utmost point bore dia is 370～500mm, and thickness is 0.24mm; The 4th layer adopts plane to be wound around, and being wound around utmost point bore dia is 610～740mm, and thickness is 0.34mm; Layer 5 adopts plane to be wound around, and being wound around utmost point bore dia is 750～980mm, and thickness is 0.42mm; Layer 6 adopts hoop to be wound around, and width is not less than 80mm, and thickness is 0.5mm.
Step 34: solidify and surfacing: the liner (1) that will be wound with carbon fiber composite layer (4) is warmed up to 120 ± 5 ℃, is incubated 50～70min, cooling with stove.
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104648696A (en) * | 2014-12-11 | 2015-05-27 | 上海空间推进研究所 | Metal propellant storage tank for spaceflight and manufacturing method thereof |
| CN105179106A (en) * | 2015-06-26 | 2015-12-23 | 北京宇航系统工程研究所 | Butt flange strengthening structure |
| CN105674041A (en) * | 2016-01-28 | 2016-06-15 | 上海空间推进研究所 | Spherical composite gas cylinder for spaceflight |
| CN106369276A (en) * | 2016-09-30 | 2017-02-01 | 上海空间推进研究所 | Equator installation spherical pressure container mounting flange structure and preparation method thereof |
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| CN109973248A (en) * | 2019-05-06 | 2019-07-05 | 上海空间推进研究所 | A kind of tank shell with versatile interface |
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| CN111037083A (en) * | 2019-12-12 | 2020-04-21 | 西安航天发动机有限公司 | Vacuum electron beam welding method for aluminum alloy metal diaphragm storage tank |
| CN112389682A (en) * | 2020-11-11 | 2021-02-23 | 上海空间推进研究所 | Diaphragm storage box |
| CN112664820A (en) * | 2020-12-16 | 2021-04-16 | 上海空间推进研究所 | Composite flange for spacecraft composite material pressure vessel and manufacturing method thereof |
| CN113059325A (en) * | 2021-03-31 | 2021-07-02 | 贵州航天天马机电科技有限公司 | Precision forming method for large-size variable-curvature thin-wall storage tank diaphragm |
| CN113479348A (en) * | 2021-07-02 | 2021-10-08 | 兰州空间技术物理研究所 | Membrane sealing and clamping assembly capable of achieving real-time and efficient discharge in multi-dimensional high-speed flight |
| CN113768272A (en) * | 2014-03-14 | 2021-12-10 | 奥布里斯特封闭瑞士有限公司 | Improvements in or relating to deodorising balls |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6231008B1 (en) * | 1998-03-12 | 2001-05-15 | Daimlerchrysler Aerospace Ag | Method and liquid storage tank for minimizing permeation of liquid vapors through a tank dividing membrane |
| CN1715729A (en) * | 2005-07-04 | 2006-01-04 | 哈尔滨工业大学 | Composite material pressure container with large size, super thin metal inner lining and its producing method |
| CN102672880A (en) * | 2012-05-04 | 2012-09-19 | 华为终端有限公司 | Carbon fiber member manufacturing method and carbon fiber member manufactured by method |
| CN203594528U (en) * | 2013-07-25 | 2014-05-14 | 上海空间推进研究所 | Carbon fiber composite metal film storage box |
-
2013
- 2013-07-25 CN CN201310317822.8A patent/CN103437913B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6231008B1 (en) * | 1998-03-12 | 2001-05-15 | Daimlerchrysler Aerospace Ag | Method and liquid storage tank for minimizing permeation of liquid vapors through a tank dividing membrane |
| CN1715729A (en) * | 2005-07-04 | 2006-01-04 | 哈尔滨工业大学 | Composite material pressure container with large size, super thin metal inner lining and its producing method |
| CN102672880A (en) * | 2012-05-04 | 2012-09-19 | 华为终端有限公司 | Carbon fiber member manufacturing method and carbon fiber member manufactured by method |
| CN203594528U (en) * | 2013-07-25 | 2014-05-14 | 上海空间推进研究所 | Carbon fiber composite metal film storage box |
Cited By (22)
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|---|---|---|---|---|
| CN113768272A (en) * | 2014-03-14 | 2021-12-10 | 奥布里斯特封闭瑞士有限公司 | Improvements in or relating to deodorising balls |
| CN104648696A (en) * | 2014-12-11 | 2015-05-27 | 上海空间推进研究所 | Metal propellant storage tank for spaceflight and manufacturing method thereof |
| CN104648696B (en) * | 2014-12-11 | 2017-01-04 | 上海空间推进研究所 | Space metal propellant tank and manufacture method thereof |
| CN105179106A (en) * | 2015-06-26 | 2015-12-23 | 北京宇航系统工程研究所 | Butt flange strengthening structure |
| CN105674041A (en) * | 2016-01-28 | 2016-06-15 | 上海空间推进研究所 | Spherical composite gas cylinder for spaceflight |
| CN106369276A (en) * | 2016-09-30 | 2017-02-01 | 上海空间推进研究所 | Equator installation spherical pressure container mounting flange structure and preparation method thereof |
| CN106369276B (en) * | 2016-09-30 | 2019-01-18 | 上海空间推进研究所 | Equator is installed by globular pressure-container mounting flange structure and preparation method thereof |
| CN106586035A (en) * | 2016-12-09 | 2017-04-26 | 大连理工大学 | Launch vehicle low-temperature composite storage tank with triangular sandwich wall and processing method of tank |
| CN106586035B (en) * | 2016-12-09 | 2018-11-13 | 大连理工大学 | Carrier rocket low-temperature composite material tank and its processing method with triangular sandwich wall |
| CN107323695A (en) * | 2017-06-14 | 2017-11-07 | 贵州航天朝阳科技有限责任公司 | A kind of attachment structure of tank diaphragm and tank housing |
| CN109973248B (en) * | 2019-05-06 | 2021-07-13 | 上海空间推进研究所 | Storage tank shell with multifunctional interface |
| CN109973248A (en) * | 2019-05-06 | 2019-07-05 | 上海空间推进研究所 | A kind of tank shell with versatile interface |
| CN110748785A (en) * | 2019-09-13 | 2020-02-04 | 上海空间推进研究所 | Metal and non-metal composite lining fiber winding composite material gas cylinder and manufacturing method thereof |
| CN111037083A (en) * | 2019-12-12 | 2020-04-21 | 西安航天发动机有限公司 | Vacuum electron beam welding method for aluminum alloy metal diaphragm storage tank |
| CN111037083B (en) * | 2019-12-12 | 2021-10-15 | 西安航天发动机有限公司 | Vacuum electron beam welding method for aluminum alloy metal diaphragm storage tank |
| CN112389682A (en) * | 2020-11-11 | 2021-02-23 | 上海空间推进研究所 | Diaphragm storage box |
| CN112389682B (en) * | 2020-11-11 | 2022-04-01 | 上海空间推进研究所 | Diaphragm storage box |
| CN112664820A (en) * | 2020-12-16 | 2021-04-16 | 上海空间推进研究所 | Composite flange for spacecraft composite material pressure vessel and manufacturing method thereof |
| CN112664820B (en) * | 2020-12-16 | 2022-04-01 | 上海空间推进研究所 | Composite flange for spacecraft composite material pressure vessel and manufacturing method thereof |
| CN113059325A (en) * | 2021-03-31 | 2021-07-02 | 贵州航天天马机电科技有限公司 | Precision forming method for large-size variable-curvature thin-wall storage tank diaphragm |
| CN113059325B (en) * | 2021-03-31 | 2023-01-20 | 贵州航天天马机电科技有限公司 | Precision forming method for large-size variable-curvature thin-wall storage tank diaphragm |
| CN113479348A (en) * | 2021-07-02 | 2021-10-08 | 兰州空间技术物理研究所 | Membrane sealing and clamping assembly capable of achieving real-time and efficient discharge in multi-dimensional high-speed flight |
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